Wing for aircraft



y 1929- A. E. 1.. CHORLTON ET AL 1,712,812

v WING FOR AIRCRAFT Filed July 16, 1928 naslr .tltlLAN ERNW'JL LEUFRICCHORLTOI T, ROLLO AMY-MEET DE HAGA I-IAIG, AND HELMUI JUHN STIEGER,0FL0NDQI i IENGLAND.

WING non Atacama.

Application filed July 16, 1928;, Serial No. 293,094, ariddzr GreatBritain December 5, 1927.

This invention relates to wings for aircraft, and more particularly to'cantilever wings in whicha spar or spars projecting from a fuselagesupport the wing formed around such spar or spars.

Spars employed as cantilevers in monoplane wings, are required to takenot only the stresses due to the vertical and horizontal bendingmomentsand combinations of these stresses, but also torsional stresses which.tend to twist thev wing, and this has necessitated the employment of aspar or pair or spars of considerable width, Which,owing to thelimitation of wing depth, have been dificult to brace satisfactorilyagainst torsion stresses.

According to this invention, a-spar is constructed of a depth.permissible by the thick ness of the wing and of any convenient width.Atsuitable positions along thespar opposed pyramid-bracings orv stayingbays through the spar.

: and

are formed projecting fore and aft from the spar with thebases of thepyramids coinciding. The apices of the pyramids are heldapart by strutspassing transversely Two pairs of tension members form the edges of eachpyramid and connect the apex of the pyramid to the upper andlower boomsor members ofthe' spar. i i v In the accompanying drawings: Figure 1 1sa dlagrammatlc section oi: a wing of an aircraft containing a spar con-'structed in accordance with this invention.

Figure 2 is adiagrammatic perspective view of the same spar.

The spar is illustrated in girder form, A being the u per boom, B beingthe lower boom and 6 representing the web of the girder. The pyramidbracings will be seen to form staying bays on opposite sides of thegirder and are composed of struts D, D.

--The tension members are illustrated in pairs E E and F, F forming onebay,

(id and H, H forming the opposite ba l 'lhe strut D passes through anaperture C in the web O and is thus free and unconnected to the web 0,or tothe spar, except through the tension members E, E F, P, G, G H, H

The tension members are illustrated in the drawings aswires, but it isobvious that tubes or other more rigid connections may be used-in theplace of the said wires.

to take bending K isa longitudinal wire connecting the ends of thestruts D of the spar on one side tl1ereof,and L is a similar wlreconnecting the other ends of the struts D on the opposite side of thespar.

The struts which maintain the apices of the pyramids apart, may beformed by straight-poles or triangular frames, and when the centres ofthe pyramids coincide with the ribs or with frames arranged in thedirection of the chord of the Wing, such ribs or frames may be utilizedafter being,

suitably strengthened for supporting the apiceso'f the pyramids andtaking the tension of the tension members located on the tension membersare convenientlymade-of wire, and it will be clearly recognized that thetension members comprising the bays nearest to the fuselage will berequired to support greater stress than the wires comprising tensionmembers in the outer bays away from the fuselage. The thickness of: thewires should therefore be chosen in accordance with the distance of thebay from the centre of the machine, larger gauge wires being usednear'the fuselage and less gauge wires'being used in the outer. bays.

What We claim as our invention and de sire to secure by Letters Patentis l. Cantilever spars for aircraft adapted stresses and torsionalstresses, comprising in combination, upper and lower booms, aweb-attached to and holding such booms apart, and pyramid bracing-sconstituting bays on opposite sides of the girder, each opposed pair ofbays consisting of a compression member passing stresses, comprising incombination, upper and lower booms, a web attached to and holding suchbooms apart, and pyramid bracings, constituting bays on opposite sidesof the girder each opposed pair of bays consisting of a compressionmember passing transversely through the said web, and four tensionmembers connecting each end of ..lo I

each boom such separated points being 1osuch compression member to thebooms.

3. Cantilever spars for' aircraft adapted to take bending stresses andtorsional stresses, comprising in combination, upper and lower booms, aweb attached to and holding such 'boom's apart and pyramid bracingsconstituting bays on opposite sides of the girder each opposed pair ofbays consisting of compression supports projecting on o posite sides ofthe girder and tension mem rs connecting the apices of the compressionsupports to twoseparated points on cated on the booms on opposite sidesof a plane containing both apices and perpendicularito the main axis ofthe spar.

to take bending 4.-'Cantilever spars for aircraft adapted stresses andtorsional stresses, comprising in combination, upper and lower booms, aweb attached to'.and holding such booms apart, and. pyramid braoingsconstituting bays on opposite sides of the girder each opposed pair ofbays consisting of struts passing transversely through the web of thespar and projecting on o posite sides of the girder, and tension mem rsconnecting the opposite ends of the said strut to separated lnts oneachboom.

5. Cantilever spars or aircraft adapted to i take bending stresses andtorsional stresses, comprising in combination, upper and lower booms, aweb attached to and holding such booms apart, and yramid bracingsconstituting bays on opposite sides of the girder each oppoM pair of baconsistingof-struts passing transverse y and freely throu h the web ofthe spar and proand tension mem rs connecting theopposite ends of thesaid strut to separated I points on each boom.

In witness whereof our hands.

ALAN ERNEST LEQI'IIC noun Ann-r a. IAGA lmc. llI-ILIUI 10ml 5mm.

46 jecting on t e op ite sides of the girder,

we have hereunto set

